An in-flight correction algorithm of alignment errors is proposed to reduce the navigation errors for the vehicle with a strapdown inertial navigation system (SINS) and a Global Navigation Satellite System (GNSS), when the GNSS is disabled. The system equations and measurement equations are derived in launch centered inertial coordinate system, and the the Kalman filter is used to estimate the misalignment angles in-flight. Simulations, which show the validity of the algorithm in estimating and correcting alignment errors, are presented to illustrate the improvement of navigation performance in case of the GNSS is unavailable.


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    Title :

    In-flight correction of alignment errors for SINS/GNSS integrated navigation system


    Contributors:
    Luyang Liang (author) / Feng Zhou (author) / Ye Yang (author) / Tao Guo (author)


    Publication date :

    2016-08-01


    Size :

    357359 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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